Fiber optic directional sensor and method

ABSTRACT

A fiber optic directional sensor has a substantially hemispherical dome surface and a substantially flat surface. The sensor is formed from a plurality of optical fibers fused to one another, and each optical fiber extends from the dome surface to the flat surface. One end of each optical fiber is substantially perpendicular to the sensor&#39;s dome surface, and the opposite end of the fiber is substantially perpendicular to the sensor&#39;s flat surface such that an end face of the fiber is substantially tangent to the dome surface, and another end face of the fiber is substantially tangent to the flat surface. Using the sensor, light from projectiles, such as missiles, bullets, and other weaponry, can be detected, and the locations of the projectiles can be determined.

CROSS REFERENCE TO RELATED APPLICATION

This application claims priority to U.S. provisional patent application No. 61/437,953, entitled “UAV Dome Launch Sensors” and filed on Jan. 31, 2011, which is incorporated herein by reference.

STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT

This invention was made with Government support under W91CRB-10-P-0030 awarded by the U.S. Army Aviation and Missile Research Development and Engineering Center (AMRDEC). The Government has certain rights in the invention.

RELATED ART

Launch detection based on light from projectiles, such as, for example, plumes during boost from ballistic missiles or rocket-propelled grenades (RPGs), or muzzle flashes from .50-caliber rifles, is of great concern in military applications. Launch detection of such projectiles is typically done using conventional imaging sensors which are often complex, bulky, heavy, and expensive (e.g., large aperture telescopes having lenses and/or mirrors). Such conventional optics are capable of providing high resolution images of the projectiles but often have a very narrow field of view (FOV), for example, under one degree.

Ballistic missile launch detection is often done from aircraft in order to locate launch sites. Conventional launch sensors are typically positioned on large aircraft in order to accommodate the size and weight of the launch sensors. However, the use of large aircraft for launch detection in military applications is undesirable due to the easy detection of such aircraft by enemies. Furthermore, due to the narrow field of view of the conventional launch sensors, the large aircraft typically perform launch detection from very large stand-off distances. Such large distances may compromise the ability of the conventional launch sensor to accurately detect all of the projectiles launched by the enemy. Thus, conventional launch sensors have significant drawbacks in launch detection.

BRIEF DESCRIPTION OF THE DRAWINGS

The disclosure can be better understood with reference to the following drawings. The elements of the drawings are not necessarily to scale relative to each other, emphasis instead being placed upon clearly illustrating the principles of the disclosure. Furthermore, like reference numerals designate corresponding parts throughout the several views.

FIG. 1 is a side cutaway view of an exemplary fiber optic directional sensor in accordance with the present disclosure.

FIG. 2 is a perspective view of another exemplary fiber optic directional sensor in accordance with the present disclosure.

FIG. 3 is a top view of the fiber optic directional sensor of FIG. 2.

FIG. 4 is a side view of the fiber optic directional sensor of FIG. 2.

FIG. 5 is a side cutaway view of the fiber optic directional sensor of FIG. 2 depicting optical fibers within the sensor.

FIG. 6 is an end view of an exemplary optical fiber, such as is depicted by FIG. 5.

FIG. 7 is an end view of an exemplary bundle of a plurality of optical fibers.

FIG. 8 is an end view of an array of optical fibers.

FIG. 9 is a side view of an optical fiber during the drawing process.

FIG. 10 is a side view of a block of fused optical fibers during the manufacture of a fiber optic directional sensor, such as is depicted by FIG. 2.

FIG. 11 is a side view of the block of FIG. 10 after the block has been stretched.

FIG. 12 is a block diagram depicting an exemplary fiber optic directional sensing system.

FIG. 13 is a block diagram depicting another exemplary fiber optic directional sensing system.

FIG. 14 is a flowchart illustrating an exemplary fiber optic directional sensing method.

FIG. 15 depicts a bright spot on the flat surface of the sensor 10 of FIG. 2.

DETAILED DESCRIPTION

Embodiments of the present disclosure generally pertain to fiber optic directional sensors. An exemplary fiber optic directional sensor comprises a substantially hemispherical dome surface and a substantially flat surface. The sensor is formed from a plurality of optical fibers fused to one another. Each optical fiber extends from the dome surface to the flat surface. One end of each optical fiber is substantially perpendicular to the sensor's dome surface, and the opposite end of the fiber is substantially perpendicular to the sensor's flat surface such that an end face of the fiber is substantially tangent to the dome surface, and another end face of the fiber is substantially tangent to the flat surface.

FIG. 1 depicts an exemplary embodiment of a fiber optic directional sensor 5. The sensor 5 comprises a dome surface 6 and a flat surface 7. As shown by FIG. 1, the dome surface 6 is substantially hemispherical. The sensor 5 comprises a plurality of optical fibers 8 extending from the dome surface 6 to the flat surface 7. FIG. 1 depicts only five optical fibers 8 for illustrative purposes, but the sensor 5 may comprise a large number (e.g., millions) of fibers 8. In one embodiment, the fibers 8 comprise glass, but other materials are possible in other embodiments. The fibers 8 may be fused to one another in a manufacturing process, described in more detail hereafter, in order to form the sensor 5.

Each optical fiber 8 extends from a point on the dome surface 6 to a corresponding point on the flat surface 7. Note that an end face (not shown) of each optical fiber 8 forms a part of the dome surface 6 such that a centerline 9 running along the fiber 8 is substantially perpendicular to the dome surface 6 at the end face. Another end face (not shown) of the fiber 8 forms a part of the flat surface 7 such that the centerline 9 running along the fiber 8 is substantially perpendicular to the flat surface 7 at such end face. In this regard, the opposing end faces of each optical fiber 8 are substantially flat and substantially perpendicular to the centerline 9 running along the fiber 8. Thus, one end face of each fiber 8 is substantially tangent to the dome surface 6 such that an angle between the centerline 9 and the surface 6 is approximately 90 degrees, and the other end of the fiber 8 is substantially tangent to the flat surface 7 such that an angle between the centerline 9 and the surface 7 is approximately 90 degrees. Accordingly, each fiber 8 has a narrow FOV that makes up a portion of the entire, broad FOV for the sensor 5. Note that FIG. 1 shows a narrow FOV for one of the fibers 8. Each of the other fibers 8 would similarly have a narrow FOV extending along a centerline 9 of the respective fiber's core.

The narrow FOV for each fiber 8 corresponds to a particular azimuth and elevation. In this regard, any light detected by a particular fiber 8 at the dome surface 6 is propagated through the fiber 8 to the flat surface 7. Based on the position of the light on the flat surface 7, the azimuth and elevation of the light with respect to the sensor 5 can be determined, as will be discussed in more detail hereafter.

FIG. 2 depicts another exemplary embodiment of a fiber optic directional sensor 10.

The sensor is configured to detect objects and to indicate a direction in which the objects are detected, as will be discussed in more detail hereafter. In one embodiment, the sensor 10 is configured for use in launch detection of projectiles, such as, for example, missiles, rocket-propelled grenades (RPGs), or muzzle flashes (e.g., from .50-caliber rifles), but other applications are possible in other embodiments. As shown by FIG. 2, the sensor 10 comprises a substantially hemispherical dome surface 12 and a tapered neck 14. The neck 14 extends downwardly from a peripheral edge of the dome surface 12 and tapers inwardly to a peripheral edge of a substantially flat surface 15. In this regard, a diameter of the dome surface 12 is sufficiently greater than a diameter of the flat surface 15 such that the neck 14 tapers inwardly as the neck 14 extends from the peripheral edge of the dome surface 12 to the peripheral edge of the flat surface 15. In one embodiment, a diameter of the dome surface 12 is approximately 26 millimeters (mm), and a diameter of the flat surface is approximately 5 mm. Furthermore, in one embodiment, a length of the sensor 10 from a top of the dome surface 12 to the flat surface 15 is approximately 35 mm. However, other dimensions are possible in other embodiments. The sensor 10 comprises a plurality of optical fibers (not shown in FIG. 2) fused to one another, as will be discussed in more detail hereafter. In one embodiment, the sensor 10 comprises glass, although different materials are possible in other embodiments.

Each optical fiber has a narrow field of view (FOV) in which the fiber can detect light, as will be discussed in more detail hereafter. In this regard, an end face (not shown in FIG. 2) of each fiber forms a part of the dome surface 12 and makes up a small portion of a total FOV for the dome surface 12. Due to the substantially hemispherical shape of the dome surface 12, the total FOV for the sensor 10 is relatively large. In one embodiment, the total FOV for the dome surface 12 is approximately 90 degrees (e.g., plus or minus approximately 45 degrees), but different FOVs are possible in other embodiments.

The sensor 10 is relatively small and lightweight thereby enabling launch detection from small aircraft, such as, for example, unmanned air vehicles (UAVs). In this regard, the aircraft can perform launch detection from close stand-off distances as opposed to the long stand-off distances typically used for the large aircraft carrying conventional launch sensors (not shown). Furthermore, the relatively large FOV of the sensor 10 as compared to the small FOV of conventional launch sensors allows the sensor 10 to detect objects in a wide range of directions. Also, a plurality of sensors 10 may be positioned on the aircraft in order to enable simultaneous launch detection of a plurality of different types of objects, as will be discussed in more detail hereafter.

FIG. 3 depicts a top view of the fiber optic directional sensor 10 of FIG. 2. As shown by FIG. 3, the dome surface 12 is substantially circular and convex. As set forth above, the convex shape of the dome surface 12 allows the sensor 10 to have a relatively large FOV as compared to conventional launch sensors (not shown). In one embodiment, the sensor 10 has a field of view of plus-or-minus approximately 45 degrees, but other FOVs are possible in other embodiments. Thus, the sensor 10 detects light from a wide area and automatically indicates the direction from which the light was received based on which optical fibers (not shown in FIG. 3) detected the light, as will be discussed in more detail hereafter. Furthermore, the sensor 10 may simultaneously detect light from multiple bright objects and automatically indicate the direction of the light from each object.

FIG. 4 depicts a side view of the sensor 10 of FIG. 2. The sensor 10 comprises the dome surface 12, the tapered neck 14, and the flat surface 15, as set forth above. A perimeter of flat surface 15 is substantially circular, and the neck 14 gradually tapers from a peripheral edge of the dome surface 12 to a peripheral edge of the flat surface 15. As shown by FIG. 4, a diameter of the dome surface 12 is significantly larger than a diameter of the flat surface such that light received through the relatively large dome surface 12 is transferred to the smaller flat surface 15 via the neck 14 and is thereby easier to analyze, as will be discussed in more detail hereafter. In this regard, the sensor 10 receives light through the dome surface 12 and optical fibers (not shown in FIG. 4) within the sensor 10 guide the light from the dome surface 12 to the flat surface 15. Thus, the sensor 10 receives light from a broad area via the dome surface 12 and the light is automatically transferred to the flat surface 15 via the optical fibers.

FIG. 5 depicts a cutaway view of the sensor 10 of FIG. 2. The sensor 10 comprises a plurality of optical fibers 20 extending from the dome surface 12 to the flat surface 15. FIG. 5 depicts only five optical fibers 20 for illustrative purposes, but the sensor 10 typically comprises a large number of fibers 20. Indeed, in one embodiment, a large number of optical fibers 20 (e.g., about 2.8 million) are fused together in a manufacturing process, such as, for example, a conventional multi fiber drawing process, as will be described in more detail hereafter, to form the dome-shaped sensor 10 depicted by FIGS. 1-4. However, other numbers of fibers 20 are possible in other embodiments.

Each optical fiber 20 extends from a point on the dome surface 12 to a corresponding point on the flat surface 15. Note that an end face (not shown in FIG. 5) of each optical fiber 20 forms a part of the dome surface 12 such that a centerline 21 running along the fiber 20 is substantially perpendicular to the dome surface 12 at the end face. Furthermore, another end face (not shown in FIG. 5) of the fiber 20 forms a part of the flat surface 15 such that the centerline 21 running along the fiber 20 is substantially perpendicular to the flat surface 15 at such end face. In this regard, the opposing end faces of each optical fiber 20 are substantially flat and substantially perpendicular to the centerline 21 running along the fiber 20. Thus, one end face of each fiber 20 is substantially tangent to the dome surface 12 such that an angle between the centerline 21 and the surface 12 is approximately 90 degrees, and the other end of the fiber 20 is substantially tangent to the flat surface 15 such that an angle between the centerline 21 and the surface 15 is approximately 90 degrees. Accordingly, each fiber 20 has a narrow FOV that makes up a portion of the entire FOV for the sensor 12. In this regard, light from a projectile is incident on the ends of a plurality of contiguous fibers 20, and each such fiber 20 carries a respective portion of the light to a respective area of the flat surface 15. As an example, the light may appear as a dot on the flat surface 15, and the location of such dot within the flat surface 15 indicates the projectiles direction from the sensor 12, as will be described in more detail below. Note that a large number of the fibers 20 are curved such that the respective centerlines 21 are perpendicular to the respective surfaces 12 and 15.

The narrow FOV for each optical fiber 20 corresponds to a particular azimuth and elevation. In this regard, any light detected by a particular optical fiber 20 is received through the dome surface 12 and propagated through the fiber 20 to the flat surface 15. Based on the location of the light on the flat surface 15, the azimuth and elevation of the light with respect to the sensor 10 can be determined. More than one fiber 20 may detect the light, but the light may be brightest in the fiber 20 whose FOV is aimed most directly at the light. The azimuth and elevation for the light may be determined based on which fiber or fibers 20 transmit the brightest light, as will be discussed in more detail hereafter. Thus, the sensor 10 detects light emitted by objects and automatically indicates the direction from which the light is detected based on which optical fibers 20 received the light. Furthermore, if the light moves with respect to the sensor 10, the light is detected by one or more different optical fibers 20 in the sensor 10 which correspond to different narrow FOVs (e.g., different azimuth and elevation). Accordingly, the sensor 10 automatically tracks the movement of the light based on which optical fibers 20 detect the light over time.

In one embodiment, each optical fiber 20 comprises glass, but other materials are possible in other embodiments. Each optical fiber 20 comprises a core (not shown in FIG. 5) and cladding (not shown in FIG. 5), discussed in more detail hereafter. The optical fibers 20 are fused to one another to form the sensor 10, as will be discussed in more detail hereafter. Thus, the sensor 10 comprises the fused fibers 20 wherein each fiber 20 extends from the dome surface 12 to the flat surface 15.

FIG. 6 depicts an end face 22 of an optical fiber 20. As set forth above, the fiber 20 has two end faces 22 such that one end face 22 forms a portion of the dome surface 12 (FIG. 2) and the other end face 22 forms a portion of the flat surface 15 (FIG. 2). In one embodiment, the fiber 20 is five-sided, but other shapes are possible in other embodiments. Each fiber 20 comprises a core 23 and cladding 24. In this regard, the core 23 is dimensioned to fit within the cladding 24. In one embodiment, the cladding 24 is pre-fabricated and the core 23 is inserted into the cladding 24 such that the core 23 fits tightly within the cladding 24. However, other methods for forming the fiber 20 are possible in other embodiments. The core 23 is configured to propagate light received by the fiber 20, and the cladding 24 is configured to reflect the light such that light is guided through the core 23 from one end face 22 of the fiber 20 to the other.

The fiber 20 has an instantaneous, narrow FOV such that light entering the FOV is propagated along the fiber 20 to the flat surface 15. The fiber 20 corresponds to a specific direction (e.g., azimuth and elevation), and light detected by the fiber 20 indicates the specific direction of the light, as set forth above. As a whole, the fibers 20 transfer the light incident to the dome surface 12 to the flat surface 15, and each fiber 20 carries a respective portion of such light. Since the area of the flat surface 15 is smaller than that of the dome surface 12, the size of the light at the flat surface 15 is reduced in proportion to the ratio of the surface areas.

FIG. 7 depicts a bundle 30 of optical fibers 20. In one embodiment, the bundle 30 comprises four optical fibers 20 and an interstitial rod 33 between the fibers, but different numbers of optical fibers 20 are possible in other embodiments. As shown by FIG. 7, the fibers 20 are positioned in a square bundle 30 and the rod 33 is positioned in a space between the fibers 20. The rod 33 is configured to absorb stray light from the fibers 20 such that the stray light is not transmitted to the other fibers 20 thereby reducing crosstalk between the fibers 20. In this regard, stray light from one fiber 20 may be transmitted to one or more other fibers 20 in the bundle 30 thereby reducing the ability of the sensor 10 (FIG. 2) to accurately detect the direction of the light. In one embodiment, the rod 33 comprises black glass configured to absorb stray light, but different materials are possible in other embodiments. Thus, the rod 33 absorbs the stray light and increases the accuracy of the detections made by the sensor 10.

In one embodiment, a plurality of fibers 20, such as for example, approximately 10-12 fibers 20, on the flat surface 15 (FIG. 2) correspond to a pixel of a light sensing apparatus (not shown in FIG. 7), discussed in more detail hereafter. Thus, if one or more of such fibers 20 detect light above a threshold, the pixel indicates that light from a specific direction is detected.

FIG. 8 depicts an array 40 of optical fibers 20. The array 40 comprises a plurality of bundles 30 of optical fibers 20. The array 40 of FIG. 8 comprises 36 bundles 30 and 144 fibers 20 for illustration, but different numbers of bundles 30 and fibers 20 are possible in other embodiments. For example, in one embodiment, the array 40 comprises approximately 700,000 bundles and approximately 2.8 million fibers 20. The array 40 spans the entire flat surface 15 and the entire dome surface 12. In this regard, each fiber 20 gradually decreases in area as it approaches the flat surface 15 such that there is a 1:1 ratio of fibers 20 contacting the flat surface 15 to fibers 20 contacting the dome surface 12. As set forth above, each fiber 20 has a narrow FOV, and each narrow FOV makes up a portion of the total FOV for the array 40. Thus, the array 40 covers a wide area, and light from objects in the FOV of the array 40 is detected by the sensor 10.

Exemplary techniques for manufacturing a sensor 10 according to an exemplary multi-fiber drawing process developed and/or implemented by Schott North America, Inc. will be described in more detail below.

In this regard, FIG. 9 depicts a side view of an optical fiber 20 during a drawing process. Each optical fiber 20 is assembled individually, and the cross-section of the optical fiber 20 is initially much larger than the cross-section of the fiber 20 in its final form in the sensor 10 (FIG. 2). That is, the cross-section of each fiber 20 is decreased during manufacturing. In this regard, in one embodiment, the fiber 20 is fed into a furnace 42 and heated until the fiber 20 becomes soft. The fiber 20 is then drawn out of the furnace 42 via a pulling mechanism 45 at a relatively high speed, thereby drastically decreasing the cross-section of the fiber 20 while maintaining the shape. The fiber 20 is then cooled and hardened.

Once the fiber 20 is hardened after the initial drawing process, the fiber 20 is assembled into a stack (not shown) with a plurality of other fibers 20 and a plurality of rods 33 (FIG. 7). The assembled stack is then fed through the furnace 42 until the fibers 20 and rods 33 become soft. Once the fibers 20 and rods 33 become soft, they are drawn out of the furnace 42 at a relatively high speed by the pulling mechanism 45, as set forth above. The fibers 20 and rods 33 are fused to one another in the furnace 42 and the pulling mechanism 45 decreases the cross-section of the fibers 20 thereby forming a multi-fiber stack (not shown). The multi-fiber stack is then assembled into a larger stack (not shown) with a plurality of other multi-fiber stacks. This larger stack is fed through the furnace 42, the smaller stacks that have been assembled are fused to one another, and the fused multi-fiber stack are drawn out by the pulling mechanism 45 at a relatively high speed thereby decreasing the cross-section of the fibers 20 within the stack. This process is repeated until a block (not shown in FIG. 9) having a large number (e.g., hundreds of thousands or millions) of fused optical fibers 20 is formed. The block may then be formed into one or more sensors 10, as will be discussed in more detail hereafter.

FIGS. 10 and 11 depict a block 50 of fused optical fibers 20 (FIG. 5) during the manufacturing process. Once an adequate number of optical fibers 20 are assembled, the fibers 20 are fused to one another to form the block 50, as set forth above. The block 50 comprises a plurality of substantially parallel optical fibers 20 extending from one end of the block 50 to another. In one embodiment, the block 50 may be formed into a cylindrical shape, as shown by FIG. 10. However, the block 50 may have other shapes, such as, for example, square or rectangular shapes, in other embodiments. Once the block 50 is formed into the desired shape, the block 50 is heated and gradually pulled apart at opposing ends 54 such that a tapered region 52 is formed in the middle of the block 50, as shown by FIG. 11. The tapered region 52 stretches and gradually tapers from the opposing ends 54 of the block such that a diameter of the tapered region 52 is smallest at its centermost point, and the diameter of the tapered region 52 increases as the tapered region 52 approaches the opposing ends 54 of the block 50.

Once the block 50 is stretched such that the tapered region 52 is formed, one or more sensors 10 (FIG. 2) may be formed from the block 50. For example, two sensors 10 may be formed from the block 50 shown in FIG. 11. In this regard, the sensors 10 may be formed from the tapered region 52 such that the neck 14 (FIG. 2) of each sensor 10 corresponds to a portion of the tapered region 52. The flat surface 15 (FIG. 2) of each sensor 10 is formed by cutting the block 50 near a center of the tapered region 52 at about point 53 in FIG. 11. Note that the flat surface 15 is substantially perpendicular to the centerline 21 (FIG. 5) of the optical fibers 20 (FIG. 5).

The dome surface 12 (FIG. 2) of each sensor 10 is also formed from the block 50. In this regard, the block 50 is cut in the tapered region 52 near one of the ends 54 such that the dome surface 12 corresponds to the dotted reference line 55 in FIG. 11 after grinding and polishing of the dome surface 12 are completed. The cutting, grinding, and polishing of the dome surface 12 are performed such that the centerline 21 of each optical fiber 20 is ultimately substantially perpendicular to the dome surface 12. Once the dome surface 12 and the flat surface 15 are cut for each sensor 10, any remains of the block 50 may be discarded.

FIG. 12 depicts an exemplary embodiment of a fiber optic directional sensing system 60. The system 60 comprises a fiber optic directional sensor 10, such as is depicted by FIG. 2. The system 60 further comprises a filter 62 and a light sensing apparatus 63. In one embodiment, the filter 62 abuts the flat surface 15 (FIG. 2) of the sensor 10 and the apparatus 63 abuts the filter 62. The filter 62 is configured to receive light passing through the sensor 10 and to filter the light such that only light having a certain wavelength is passed through the filter 62 to the light sensing apparatus 63. In this regard, light from a projectile, such as, for example, a missile, RPG, or .50-caliber rifle, may have a particular wavelength due to certain gases and substances released when such projectile is fired or propelled. Thus, for example, if directional sensing of missiles is desired, the filter 62 is configured to filter out other wavelengths of light such that the wavelength of light typically produced by the missile to be detected is isolated. Accordingly, any light passing through the sensor 10 that has the wavelength of light produced by the desired projectile is passed through the filter 62 to the light sensing apparatus 63.

The light sensing apparatus 63, such as, for example, a charge-coupled device (CCD), is configured to receive light from the filter 62 and to produce an output indicative of the brightness of the light. In one embodiment, the apparatus 63 comprises a plurality of pixels, and each pixel corresponds to a plurality of contiguous optical fibers 20 (FIG. 5) of the sensor 10. Light carried by a given fiber 20 illuminates its corresponding pixel. Thus, by determining which pixel or pixels sense light from an object, it can be determined which fibers 20 carry the light and, hence, the object's direction from the sensor 10 since each fiber is oriented in a specific direction at the dome surface 12.

In particular, as set forth above, each optical fiber 20 has an instantaneous, narrow FOV corresponding to a particular azimuth and elevation with respect to the sensor 10. Thus, if the optical fibers 20 corresponding to a particular pixel carry light having a certain wavelength, the light will pass through the filter 62 to the apparatus 63 causing the apparatus 63 to sense the light and assign to the pixel a brightness value indicative of the measured brightness of the light for that pixel. The apparatus 63 then compares such brightness value to a predetermined threshold. If the brightness value exceeds the threshold, the apparatus 63 indicates that a bright object has been detected for the pixel. Furthermore, in one embodiment, if the brightness values of more than one contiguous pixels exceed the threshold, then the pixel or pixels having the highest brightness value correspond to the center of the object. Therefore, the apparatus 63 automatically indicates the direction of the object with respect to the sensor 10.

The system 60 further comprises a control element 66 coupled to the light sensing apparatus 63. The control element 66 is configured to receive the indication from the apparatus 63 and to produce an output signal indicative of the location of the object. In this regard, the direction of the object from the sensor 10 can be estimated based on which fibers 20 carry light from such object and, hence, which pixels of the apparatus 63 sense such light. Further, the distance of the object from the sensor 10 can be estimated based on the magnitude of the light source.

Note that the system 60 further comprises vehicle orientation and location information 68 and an output interface 69. In one embodiment, for example, the sensor 10 is located on a vehicle, such as, for example, a UAV. The vehicle orientation and location information 68 indicates the vehicle's orientation and location relative to a geographical coordinate system in order to allow the control element 66 to determine the location of the object relative to such geographical coordinate system based on the indication from the apparatus 63. Thus, in one embodiment, the system 60 comprises an orientation sensor (not shown) and a global positioning system (not shown) for determining the precise orientation and location of the vehicle and providing the information 68. The control element 66 uses the vehicle orientation and location information 68 to determine the object's location relative to the geographical coordinate system.

In this regard, the control element 66 compares the azimuth and elevation of the object as detected by the sensor 10 with the orientation and location of the vehicle in order to determine the object's location relative to a geographical coordinate system. That is, the control element 66 translates the object's location from a coordinate system relative to the vehicle to a coordinate system relative to Earth. The logic 66 then transmits an output signal to the output interface 69 indicating the location of the object relative to Earth. In one embodiment, the output interface 69 displays a geographical map and indicates a spot on the map corresponding to the location of the object. However, different types of output interfaces 69 and output signals are possible in other embodiments. Accordingly, any object producing light of a desired wavelength is detected by the sensor 10 and transmitted to the output interface 69 in order to indicate the location of the object (e.g., azimuth and elevation) relative to a geographical coordinate system.

Note that the control element 66 may be implemented in hardware, software, firmware, or any combination thereof. In one exemplary embodiment, the control element 66 is implemented in software and stored in memory (not shown) of the system 60. In such embodiment, there may be a processing element (not shown), such as, for example, a digital signal processor (DSP) or central processing unit (CPU) for executing the control element 66.

FIG. 13 depicts another exemplary embodiment of a fiber optic directional sensing system 70. The system 70 comprises a sensor 10, a filter 62, and a light sensing apparatus 63. Note that the sensor 10, the filter 62, and the apparatus 63 are configured and operate identically to the sensor 10, the filter 62, and the apparatus 63 of FIG. 12, except as otherwise described herein. The system 70 further comprises a control element 76, a camera controller 78, and a camera 79. One or more of the optical fibers 20 (FIG. 5) of the sensor 10 detect light from an object and transmit the light to the filter 62. The filter 62 isolates light of a desired wavelength such that only light from a desired object type is passed to the apparatus 63. The apparatus 63 compares the brightness of the light to a threshold and provides an indication of the direction of the light with respect to the sensor 10. Such indication is transmitted to the control element 76.

The control element 76 receives the indication of the direction of the object from the apparatus 63 and controls the camera controller 78 and the camera 79 based upon the indication. In this regard, the sensor 10 does not capture a high resolution image of the object but only identifies bright light within the sensor's FOV. Thus, the sensor 10 may be utilized as a warning sensor in order to indicate objects of potential interest. Based on the indication from the apparatus 63, the control element 76 transmits a control signal to the camera controller 78 indicating the direction of the detected object such that the controller 78 aims the camera 79 in the direction of the object. The camera 79, such as, for example, a high-resolution digital camera, then captures images of the object such that a determination of the object's identity may be made. Accordingly, the sensor 10 acts as a warning sensor for the system 70, and the control element 76 automatically controls the camera 79 based on an indication of the object's location.

In one exemplary embodiment, assume that the sensor 10 is implemented in a fiber optic directional sensing system 60. Further assume that the sensor 10 is positioned upon a UAV, and the system 60 is configured to detect missiles. Further assume that the light sensing apparatus 63 comprises a CCD.

The fiber optic directional sensor 10 is positioned upon the UAV, as depicted by block 100 of FIG. 14, and coupled to the filter 62 and the CCD. The UAV then flies a desired course at a desired altitude, and the orientation and location of the UAV is stored in the vehicle orientation and location information 68. The information 68 is constantly tracked and updated in real time in order to provide accurate indications of the UAV's orientation and location. The sensor 10 constantly detects light entering the sensor's FOV and transmits such light to the filter 62, as shown by block 102. In this regard, each optical fiber 20 has a narrow FOV that makes up a portion of the total FOV for the sensor 10.

Now assume that a missile enters the FOV of a plurality of contiguous optical fibers 20. In this regard, and end face 22 of each of the contiguous fibers 20 is aimed at the missile while the end faces 22 of the other fibers 20 forming the dome surface 12 are not aimed at the missile due to the curvature of the dome surface 12. Light from the missile is received by the contiguous fibers 20 at the dome surface 12 and transmitted through the fibers 20 to a corresponding location on the flat surface 15. In this regard, light from the missile is carried by the contiguous fibers 20 and forms a bright spot 85 on the flat surface 15, as shown by FIG. 15. The filter 62 receives the light from the sensor 10 and filters the light such that only light having the wavelength corresponding to the desired projectile passes through the filter 62, as shown by block 104 of FIG. 14. In this regard, the filter 62 allows wavelengths of light typically produced by missiles to pass through the filter 62 and blocks all other wavelengths of light such that only light having the same wavelength of light produced by missiles is allowed to pass. Such light is passed to the pixel or pixels of the CCD corresponding to the optical fibers 20 in the bright spot 85. Note that the filtering is optional, and it is possible for the filter 62 to allow a broader range of wavelengths to pass (e.g., wavelengths for multiple types of projectiles may be in the filter's passband).

The CCD receives the light from the bright spot 85 and measures a brightness of each pixel. The CCD provides an indication of the brightness of the pixels to the control element 66. The control element 66 compares the brightness of the light for each pixel to a predetermined threshold, and provides an indication of the direction of the light that exceeds the threshold, as shown by block 106. In this regard, the control element 66 determines whether the object (e.g., missile) is significant based on the brightness of the object. For example, if the object is not sufficiently bright, the object is likely not a missile or poses no serious threat. If the brightness of the object exceeds the threshold, the control element 66 determines that the object is likely a missile. As set forth above, the CCD comprises a plurality of pixels, and each pixel corresponds to one or more contiguous optical fibers 20 of the sensor 10 having a narrow FOV corresponding to a particular azimuth and elevation. If two or more contiguous pixels of the CCD exceed the threshold, the control element 66 may determine that all of the contiguous pixels are sensing light from the same missile, and the control element 66 identifies the brightest pixel as the missile's center. The azimuth and elevation for the missile is then determined based on the brightest pixel.

The control element 66 receives the indication from the CCD, compares the indication to the vehicle orientation and location information 68, and provides an output signal indicating the location of the missile with respect to a geographical coordinate system, as shown by block 108. Upon determining the location of the missile relative to the geographical coordinate system, the control element 66 transmits an output signal to the output interface 69 indicating such location of the missile. As set forth above, in one embodiment, the output interface 69 displays a geographical map and the output signal indicates a spot on the map corresponding to the location of the missile relative to the map. The output signal is constantly updated such that the output interface 69 indicates the location of the missile relative to the map in real time. Accordingly, the system 60 automatically detects and tracks the location of the missile with respect to a geographical coordinate system. 

Now, therefore, the following is claimed:
 1. A method, comprising: providing a fiber optic directional sensor having a curved surface and a flat surface, the sensor formed from optical fibers that have been fused together via heating, wherein the optical fibers extend from the curved surface to the flat surface; receiving light from an object via a plurality of the optical fibers; directing the light through the plurality of the optical fibers to a light sensing apparatus, the light sensing apparatus having a plurality of pixels; sensing at one of the pixels a portion of the light passing through multiple ones of the optical fibers; and automatically determining a direction of the object with respect to the sensor based on the sensing.
 2. The method of claim 1, further comprising: filtering the light; and determining a location of the object with respect to a geographical coordinate system based on the orientation and location of the sensor and the direction of the object with respect to the sensor.
 3. The method of claim 2, further comprising providing an output signal indicative of the direction of the object with respect to the geographical coordinate system.
 4. The method of claim 3, further comprising: aiming a camera at the object based on the output signal; and capturing an image of the object.
 5. The method of claim 1, further comprising: simultaneously receiving light from a plurality of objects via one or more of the optical fibers; and automatically determining a respective direction of each of the plurality of objects with respect to the sensor based on the light received from the plurality of objects.
 6. A projectile sensing system, comprising: a sensor for receiving light from a launched projectile, the sensor having a curved surface, a flat surface, and optical fibers that have been fused together via heating, wherein the optical fibers extend from the flat surface to the curved surface; a light sensing apparatus having a plurality of light sensing pixels, the light sensing apparatus positioned such that the light is received and measured by the light sensing apparatus, wherein one of the pixels corresponds to a plurality of the optical fibers such that the one pixel receives a respective portion of the light from each of the plurality of the optical fibers; and a control element configured to receive a value indicative of a measurement of the light by the light sensing apparatus and to determine a direction of the projectile from the sensor based on the value.
 7. The projectile sensing system of claim 6, wherein the optical fibers are configured in a fused regularly-spaced block array.
 8. The method of claim 1, further comprising determining azimuth and elevation of the received light from the object based on which of the plurality of the optical fibers transmits a brighter light.
 9. The method of claim 1, wherein the plurality of the optical fibers are arranged in a perpendicular alignment with both the curved surface and the flat surface of the sensor.
 10. The method of claim 1, wherein the plurality of fused optical fibers are in a regularly-spaced block array.
 11. The method of claim 10, wherein each fused optical fiber in the regularly-spaced block array is perpendicular to both the curved surface and the flat surface of the sensor.
 12. The method of claim 1, wherein at least one of the optical fibers has an end face that is tangent to the curved surface, wherein the one optical fiber has a core, and wherein a centerline of the core is perpendicular to the curved surface at the end face.
 13. The method of claim 1, wherein each of the pixels corresponds to a respective direction, and wherein the determining comprises: identifying which of the pixels receive the light; and determining, based on the identifying, that the object is in the direction corresponding to one of the identified pixels.
 14. The projectile sensing system of claim 6, wherein each of the optical fibers has a first fiber end face tangent to the curved surface and a second fiber end face tangent to the flat surface of the sensor.
 15. The projectile sensing system of claim 14, wherein each optical fiber on the curved surface points in a particular azimuth and elevation direction.
 16. The projectile sensing system of claim 7, wherein each optical fiber in the fused regularly-spaced block array is perpendicular to both the curved surface and the flat surface of the sensor.
 17. The projectile sensing system of claim 6, wherein at least one of the optical fibers has an end face that is tangent to the curved surface, wherein the one optical fiber has a core, and wherein a centerline of the core is perpendicular to the curved surface at the end face.
 18. The projectile sensing system of claim 6, wherein each of the pixels corresponds to a respective direction, and wherein the control element is configured to identify which of the pixels receive the light and to determine that the object is in the direction corresponding to one of the identified pixels. 